CN114771053A - Hot isostatic pressing sintering Cf/Al-Al/Al3Preparation method of Ti layered composite material - Google Patents

Hot isostatic pressing sintering Cf/Al-Al/Al3Preparation method of Ti layered composite material Download PDF

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CN114771053A
CN114771053A CN202210460758.8A CN202210460758A CN114771053A CN 114771053 A CN114771053 A CN 114771053A CN 202210460758 A CN202210460758 A CN 202210460758A CN 114771053 A CN114771053 A CN 114771053A
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composite material
sheath
aluminum foil
plate
foil
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CN114771053B (en
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刘旭东
朱庆宣
孙旭东
王兴安
惠宇
那兆霖
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Dalian University
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/043—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/06—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/18—Handling of layers or the laminate
    • B32B38/1858—Handling of layers or the laminate using vacuum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C47/00—Making alloys containing metallic or non-metallic fibres or filaments
    • C22C47/20—Making alloys containing metallic or non-metallic fibres or filaments by subjecting to pressure and heat an assembly comprising at least one metal layer or sheet and one layer of fibres or filaments
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/02—Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
    • C22C49/04—Light metals
    • C22C49/06—Aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2250/00—Layers arrangement
    • B32B2250/42—Alternating layers, e.g. ABAB(C), AABBAABB(C)
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/558—Impact strength, toughness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2571/00—Protective equipment
    • B32B2571/02—Protective equipment defensive, e.g. armour plates, anti-ballistic clothing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

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Abstract

The invention relates to the technical field of intermetallic compound layered composite materials, and discloses a hot isostatic pressing sintered Cf/Al‑Al/Al3S1, designing the thickness and the number of layers of fiber cloth and aluminum foil/layer in a woven fiber Cf/Al composite material layer and the thickness and the number of layers of aluminum foil/plate and titanium foil/layer in an Al/Al3Ti intermetallic compound composite material layer according to the surface density requirement of the composite material; s2, cutting the materials such as the fiber cloth, the aluminum foil/plate, the titanium foil/plate and the like in the step S1 into the same design size, then arranging the materials in a certain sequence after treatment, filling the arranged materials into a low-carbon steel sheath, then flattening and sealing an exhaust tube after the sheath is vacuumized to high vacuum, and finally putting the sheath into a hot isostatic pressing furnace for hot-pressing sintering to obtain the Cf/Al-Al/Al3Ti layered composite material. The material can be used as an armor protection material by utilizing the properties of high impact resistance, low areal density and the like.

Description

Hot isostatic pressing sintering Cf/Al-Al/Al3Preparation method of Ti layered composite material
Technical Field
The invention belongs to the technical field of intermetallic compound layered composite materials, and relates to hot isostatic pressing sintered Cf/Al-Al/Al3A preparation method of Ti layered composite material.
Background
With the continuous demand of lightweight materials in high-tech fields such as aerospace, armor protection, high-speed transportation and the like, Ti-Al intermetallic compounds are more and more concerned by people due to the advantages of low density, high specific strength, high specific modulus and the like, and have wide application prospects. In the Ti-Al based intermetallic compound, Al3The Ti alloy has the lowest density (3.36 g/cm)3) The material has the advantages of highest elastic modulus (216GPa), higher melting (1360 ℃) and excellent high-temperature oxidation resistance, and is the most potential light-weight high-strength material. However, due to the stable tetragonal D022 type crystal structure, a slippage system is seriously lacked at room temperature, a strong room temperature brittleness characteristic is shown, and the engineering stress is seriously limitedThe application is as follows.
In recent years, Al has been developed3Ti/Al reinforced by high-strength titanium alloy (Ti-6Al-4V) with Ti as matrix3A Ti layered composite material. The intermetallic compound is used for providing high-temperature strength and creep resistance, and the toughness of the intermetallic compound is improved by using the ductile metal, so that the layered composite material has excellent performance. Because the intermetallic compound based laminated composite material has a unique laminated structure and a special failure mode, the composite material has the excellent performances of high strength, high modulus and low density and also has strong capacity of absorbing impact energy. Therefore, in addition to the use of intermetallic compound based layered composite materials as high temperature structural materials, developed countries in foreign countries have considered the use of the novel structural materials in armor protection systems for aviation, aerospace, weaponry and ground military vehicles, and have conducted corresponding theoretical and application foundation studies.
So far, alloying strengthening and toughening method and composite strengthening and toughening method can effectively improve Al3Room temperature plastic deformability of Ti alloys. Wherein the alloying strengthening and toughening method aims at transforming the Al into binary Al3Adding a third element into the Ti alloy to cause structural variation and strengthening and toughening to obtain the novel Al3The Ti alloy shows a certain plastic deformation characteristic at room temperature, and the variant alloy containing Cr and Mn alloy elements even shows a certain bending toughness in a bending experiment. However, the addition of the third element promotes Al3The density of Ti alloy reduces its specific strength, specific modulus and melting point. In addition, the alloying method often requires a series of processes such as high-energy ball milling, blank prefabrication, hot pressing/casting, post homogenization treatment and the like on the powder, and the preparation process is complicated. The composite strengthening and toughening method is to add Al3Introducing a tough metal Ti layer as a reinforcement into the Ti intermetallic compound to form Ti/Al3Ti layered composite material retaining Al3The D022 type crystal structure of the Ti matrix can effectively play a role in strong toughening mechanisms such as crack deflection, crack passivation, crack bridging, internal stress redistribution and the like in the crack propagation process, and effectively promotes Al3Fracture toughness of Ti alloy and its compression,The tensile stress-strain curve shows ideal plastic deformation characteristics, is a very ideal novel light high-strength structural material, and expands Al3The engineering application prospect of the Ti alloy. However, the introduction of the Ti layer of the ductile metal can obviously improve the room-temperature plastic deformation capability of the whole material, but the Ti and the Al can be used for improving the room-temperature plastic deformation capability of the whole material3At the interface of Ti, excessive Ti is easy to form a Ti3Al intermediate phase with Al, which is more brittle. Thus, during deformation, the cracks always predominate over Al3Ti layer and Ti/Al3The growth and expansion of Ti interface indicate Al3The intrinsic brittle deformation characteristics of the Ti matrix remain unchanged.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a hot isostatic pressing sintered Cf/Al-Al/Al3The preparation method of the Ti layered composite material solves the problems that the composite material obtained by the existing preparation method has large room temperature brittleness, poor interface strength, easy generation of cracks and diffusion and the like.
The above purpose of the invention is realized by the following technical scheme:
hot isostatic pressing sintering CfThe Al-Al/Al3Ti laminated composite material comprises woven fibers CfComposite layer of Al/Al, Al/Al3A Ti intermetallic compound composite layer; woven fiber Cfthe/Al composite material layer comprises a plurality of layers of fiber cloth and aluminum foils/plates which are periodically and alternately arranged; Al/Al3The Ti intermetallic compound composite material layer comprises a plurality of layers of aluminum foil/plate and titanium foil/plate which are periodically and alternately arranged.
The hot isostatic pressing sintered Cf/Al-Al/Al3The preparation method of the Ti layered composite material comprises the following steps:
s1, designing a woven fiber C according to the surface density requirement of the composite materialfThe thickness and the number of layers of the fiber cloth and the aluminum foil/plate in the Al composite material layer are designed3The thickness and the number of layers of aluminum foil/plate and titanium foil/plate in the Ti intermetallic compound composite material layer;
s2, cutting the materials such as the fiber cloth, the aluminum foil/plate, the titanium foil/plate and the like in the step S1 into the same design size, and then cuttingArranging the materials in a certain sequence after treatment, filling the arranged materials into a low-carbon steel sheath, then pumping the sheath into high vacuum, flattening and sealing an exhaust tube, and finally putting the sheath into a hot isostatic pressing furnace for hot-pressing sintering to obtain Cf/Al-Al/Al3A Ti layered composite material.
Further, the composite material in the step S1 has an areal density of 18 to 32kg/m2。
Further, the fiber cloth in the step S1 is any one of woven materials of carbon fiber, glass fiber or other high-temperature resistant fibers, and the thickness is 0.1-2 mm; the aluminum foil/plate is a pure aluminum foil or plate, and the thickness of the aluminum foil/plate is 0.1-4 mm; the titanium foil/plate is foil or plate of pure titanium or titanium alloy (Ti-6Al-4V), and the thickness is 0.1-2 mm. Wherein the purity of the pure aluminum is more than or equal to 99.5 percent; the purity of the pure titanium is more than or equal to 99.5 percent.
Further, in step S1, the fibers C are wovenfThe number of layers of the fiber cloth and the aluminum foil/plate in the/Al composite material layer is 4-15; Al/Al3The number of layers of the aluminum foil/plate and the titanium foil/plate in the Ti intermetallic compound composite material layer is 4-15.
Further, after the aluminum foil and the titanium foil which are obtained by cutting in the step S2 are polished by 1500-mesh abrasive paper, the aluminum foil and the titanium foil are respectively put into deionized water and absolute ethyl alcohol for ultrasonic treatment for 30min, and then the aluminum foil and the titanium foil are naturally dried and then put into a vacuum drying oven for drying at 50 ℃; and respectively putting the cut fiber cloth into deionized and absolute ethyl alcohol for ultrasonic treatment for 30min, naturally airing, and then putting into a vacuum drying oven for drying at 50 ℃.
Further, the arranging in a certain order as described in step S2 is to arrange the titanium foil/sheet and the aluminum foil/sheet alternately in a periodic manner, then arrange the fiber cloth and the aluminum foil/sheet alternately in a periodic manner, then stack the two arranged materials together, and finally arrange a layer of titanium foil/sheet on the outer layer of the aluminum foil/sheet.
Furthermore, the low-carbon steel refers to common steel with the carbon content of less than 0.35%, the sheath is a totally-enclosed common steel shell determined according to the size of the sample, and the gap between the interior of the sheath and the sample is required to be less than 1 mm. The high vacuum pumping of the sheath means that the pressure in the sheath is less than 5 x 10 < -3 > Pa.
Further, the step S2 of flattening and sealing the exhaust tube means that after the vacuum pumping in the sheath reaches the required vacuum degree, the exhaust tube near the sheath is heated to be softened by heating means such as acetylene flame, butane flame, electromagnetic induction coil, etc., then 3-4 impressions are flattened on the heated and softened exhaust tube by using a hydraulic clamp for sealing, finally the end of the flattened exhaust tube is cut off by a toothless saw, and the end cut off is welded by an argon arc welding machine immediately to prevent air in the atmosphere from entering the sheath.
Further, the sintering process in the hot isostatic pressing furnace in step S2 is as follows: heating the hearth temperature from 25 ℃ to 600 ℃ at a speed of 10-15 ℃/min, and introducing high-purity argon into the hearth to enable the pressure in the hearth to reach 100-120 MPa. Raising the temperature of the hearth to 700-720 ℃ at 3-5 ℃/min, introducing high-purity argon into the hearth to raise the pressure in the hearth to 150-200 MPa, wherein the final maximum temperature, maximum pressure and heating and pressurizing time depend on the type of a sample and the size of the sample. And thirdly, keeping the temperature and the pressure unchanged under the conditions of highest temperature and highest pressure, wherein the duration is 2-3 hours. Fourthly, slowly reducing the temperature and the pressure to the normal temperature and the normal pressure state after preserving the heat and the pressure.
Preparing a hot isostatic pressing sintered Cf/Al-Al/Al3Ti layered composite material by using aluminum foil, titanium foil and carbon fiber cloth as raw materials; the method specifically comprises the following steps:
preparing C in a hot isostatic pressing sintering furnace (as shown in figure 1) by using pure aluminum foil (not less than 99.5%), pure titanium foil (not less than 99.5%) and carbon fiber cloth as raw materialsf/Al-Al/Al3The Ti layered composite material comprises the following specific steps:
(1) and (5) designing a layered composite material structure. In the woven fabric CfIn the/Al composite material layer, based on the woven fibers CfCalculating the thicknesses of the carbon fiber cloth and the aluminum foil according to the percentage; in the presence of Al/Al3In the Ti intermetallic compound composite material layer, calculating the thickness of the aluminum foil and the titanium foil according to the excess percentage of Al; according to the surface density of the prepared laminated composite material, calculating the corresponding of each material in the two composite materialsThickness and number.
(2) And (3) selecting the thickness and the number of the corresponding materials according to the calculated result in the step (1), and cutting all the materials into the same size.
(3) Polishing the aluminum foil and the titanium foil obtained by cutting in the step (2) by using 1500-mesh abrasive paper, then respectively placing the aluminum foil and the titanium foil into deionized water and absolute ethyl alcohol for ultrasonic treatment for 30min, naturally airing, and then placing the aluminum foil and the titanium foil into a vacuum drying oven for drying at 50 ℃; and (3) respectively putting the carbon fiber cloth cut in the step (2) into deionized and absolute ethyl alcohol for ultrasonic treatment for 30min, then naturally airing, and then putting into a vacuum drying oven for drying at 50 ℃.
(4) And (3) stacking and arranging the materials treated in the step (3) in a manner shown in figure 2. Firstly, a layer of titanium foil is placed at the bottom, then a layer of aluminum foil in the Al/Al3Ti intermetallic compound composite material layer is placed on the titanium foil, then the titanium foil and the aluminum foil are placed in sequence until the aluminum foil in the Al/Al3Ti intermetallic compound composite material layer is used up, then the aluminum foil in the carbon fiber cloth and the woven fiber Cf/Al composite material layer is placed on the aluminum foil, then the aluminum foil is used up in the sequence, and finally a layer of titanium foil is placed on the top.
(5) According to the size of the stacked arrangement material obtained in the step (4), according to the size, a steel shell capable of tightly wrapping the stacked arrangement material is welded by a Q235 steel plate with the thickness of 2mm, the joint of the steel plates is welded and sealed by argon arc welding, and a stainless steel pipe is welded at the port to be used as an exhaust pipe, so that the sheath as shown in fig. 3 is obtained.
(6) Connecting the gas extraction pipe of the sheath obtained in the step (5) with a diffusion pump, and extracting gas to ensure that the gas pressure in the sheath is 5 multiplied by 10-3And keeping the pressure below Pa for more than 30min, heating the exhaust pipe to a softening state by using an oxygen-acetylene flame gun, flattening the softened exhaust pipe by using a hydraulic clamp for more than three times to seal, cutting off the redundant part of the exhaust pipe, and finally welding and sealing the notch by using argon arc welding.
(7) And (3) placing the sheath prepared in the step (6) into a hot isostatic pressing sintering furnace, closing a furnace door, vacuumizing a hearth to below 10Pa, cleaning the hearth three times by using high-purity argon, raising the temperature in the hearth to 600 ℃ at 10 ℃/min, introducing the high-purity argon into the hearth to enable the pressure in the hearth to reach 100MPa, raising the temperature in the hearth to 700 ℃ at 3 ℃/min, introducing the high-purity argon into the hearth to enable the pressure in the hearth to reach 150MPa, preserving heat and pressure for 3h, cooling the hearth to room temperature and discharging the argon to the outside to the ambient pressure.
(8) Opening the hot isostatic pressing sintering furnace door, taking out the sintered sheath, and cutting off the sheath by a wire cutting machine to obtain Cf/Al-Al/Al3The Ti layered composite material, a small sample, is shown in FIG. 4.
Aiming at the defects in the alloying strengthening and toughening method, the invention adopts Al3The method of Al excess 1-5% in Ti intermetallic compound replaces Cr and Mn alloy elements, eliminates the negative effects of the reduction of specific strength and specific modulus of the composite material, the increase of the complexity of the preparation process and the like, and simultaneously, the slight excess Al remains in the Al3Ti/Al3And the Ti interface avoids forming a Ti3Al brittle phase, improves the room temperature brittleness of the interface, can play a good role in connecting the interfaces, is beneficial to improving the bonding strength of the interface, has good toughness, and can effectively prevent cracks from generating and diffusing. Aiming at the defects in the composite strengthening and toughening method, the invention adopts the weaving fiber CfThe Al composite material layer replaces metals such as Al, Ti and the like, and can eliminate cracks in Al3Ti layer and Ti/Al3Ti interface growth, expansion, etc., and form CfThe fiber Al-based composite material has the characteristics of high strength and low density, and simultaneously Al-based and Al/Al can be simultaneously mixed3The Ti intermetallic compound composite layer performs good connection.
Compared with the prior art, the invention has the beneficial effects that:
(1) prepared Cf/Al-Al/Al3The Ti layered composite material has high surface hardness (greater than or equal to 580HV), high specific modulus (greater than or equal to 170GPa) and low areal density (less than or equal to 27 kg/m)2) And the tensile resistance and the compression strength are large (more than or equal to 1250MPa), and the like.
(2) In the preparation of Cf/Al-Al/Al3The Ti laminated composite material comprises woven fibers CfComposite layer of Al and Al/Al3A Ti intermetallic compound composite material layer. In the woven fabric CfIn the Al composite material layer, the carbon fiber reinforcement and the aluminum matrix both have three-dimensional communicated structural characteristics, and have good impact resistance and bending resistance; in the presence of Al/Al3In the Ti intermetallic compound composite material layer, matrix aluminum is uniformly distributed in Al3The interface between Ti intermetallic compounds can obviously reduce Al3Room temperature brittleness of Ti intermetallic compounds; the common aluminum element exists between the two layers of composite materials, so the interface bonding strength is high.
(3) Prepared Cf/Al-Al/Al3The Ti laminated composite material can be used as a functional material by utilizing the excellent performance and the anisotropy of the Ti-Al series intermetallic compound laminated composite material, for example, a mesoscale cavity or a gap can be created in different layers, and a sensing device, such as a piezoelectric element device, an accelerometer, a micro electromechanical system device and the like, can be embedded in the mesoscale cavity or the gap, and the concept of an embedded circuit is provided for the material. And the high impact resistance, low areal density and other properties of the material can be utilized to be used as an armor protection material.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a schematic view of a hot isostatic pressing sintering furnace of the AIP10-30H type.
FIG. 2 is a schematic view of the stacking arrangement of the layered composite.
Fig. 3 is a diagram of a bag.
FIG. 4 is a photograph of a small sample of a layered composite material of a Ti-Al based intermetallic compound.
FIG. 5 is an SEM photograph of a cross section of a Ti-Al based intermetallic compound layered composite material.
Detailed Description
The invention is described in more detail below with reference to specific examples, without limiting the scope of the invention. Unless otherwise specified, the experimental methods used in the present invention are conventional methods, and the experimental devices, materials, reagents, etc. used therein are commercially available.
Example 1
(1) Designing a layered composite material structure. The surface density of the prepared laminated composite material is 29g/cm2Total thickness of 10.5mm, in the laminated weaving of CfIn the/Al composite layer, according to the laminated weave CfAccounting for 40%, calculating the thicknesses of the carbon fiber cloth and the pure aluminum foil to be 0.26mm and 0.2mm respectively, and calculating the number of layers to be 7; in the presence of Al/Al3In the Ti intermetallic compound composite material layer, the thicknesses of the pure aluminum foil and the pure titanium foil are respectively 0.6mm and 0.2mm according to the excess amount of Al of 3-4%, and the number of layers is respectively 9 and 10.
(2) According to the result calculated in the step (1), selecting 7 carbon fiber cloth sheets with the thickness of 0.26mm, 7 pure aluminum foils with the thickness of 0.2mm, 9 pure aluminum foils with the thickness of 0.6mm and 10 pure titanium foils with the thickness of 0.2mm, and cutting all the materials into the same size: 120mm by 200 mm.
(3) Polishing the aluminum foil and the titanium foil which are cut in the step (2) by 1500-mesh abrasive paper, then respectively putting the aluminum foil and the titanium foil into deionized water and absolute ethyl alcohol for ultrasonic treatment, naturally airing the aluminum foil and the titanium foil, and then putting the aluminum foil and the titanium foil into a vacuum drying oven for drying at 50 ℃; and (3) respectively putting the carbon fiber cloth cut in the step (2) into deionized and absolute ethyl alcohol for ultrasonic treatment, then naturally airing, and then putting into a vacuum drying oven for drying at 50 ℃.
(4) The titanium foil of 0.2mm thickness, the aluminum foil of 0.6mm thickness, the carbon fiber cloth of 0.26mm thickness, and the aluminum foil of 0.2mm thickness treated in step (3) are respectively denoted by A, B, C, D, and then arranged in the order of ABABABABABABABABABCCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDCDA.
(5) And (5) welding the materials which are arranged in the stacking mode and obtained in the step (4) to form an open box with an inner cavity of 122mm multiplied by 200mm multiplied by 11mm by using a Q235 steel plate with the thickness of 2mm, placing the materials which are neatly stacked in the box, placing a Q235 steel plate with the inner cavity of 125mm multiplied by 205mm multiplied by 2mm on the box, welding all joints by using an argon arc welding machine, finally drilling a hole with the diameter of 8mm at the center of one end of the sheath, inserting an 8mm by 300mm stainless steel pipe, welding the stainless steel pipe and the sheath together by using the argon arc welding machine to obtain the sheath shown in the figure 3, finally connecting the stainless steel pipe by using an air compressor, and simultaneously placing the sheath in clean water to check whether the sheath is air leakage.
(6) Connecting the air exhaust pipe of the sheath which ensures air tightness in the step (5) with a diffusion pump, exhausting air, and controlling the pressure in the sheath to be 5 x 10-3And keeping the pressure below Pa for more than 30min, heating the exhaust pipe to a softening state by using an oxygen-acetylene flame gun, flattening the softened exhaust pipe by using a hydraulic clamp for more than three times to seal, cutting off the redundant part of the exhaust pipe, and finally welding and sealing the notch by using argon arc welding.
(7) And (3) putting the sheath prepared in the step (6) into a hot isostatic pressing sintering furnace, closing a furnace door, vacuumizing a hearth to below 10Pa, cleaning the hearth with high-purity argon for three times, raising the temperature in the hearth to 600 ℃ at 10 ℃/min, introducing the high-purity argon into the hearth to enable the pressure in the hearth to reach 100MPa, raising the temperature in the hearth to 700 ℃ at 3 ℃/min, introducing the high-purity argon into the hearth to enable the pressure in the hearth to reach 150MPa, keeping the temperature and the pressure for 3h, cooling the hearth to room temperature along with the furnace, and discharging the argon to the outside to reach the ambient pressure.
(8) Opening the hot isostatic pressing sintering furnace door, taking out the sintered capsule, and cutting the shell of the capsule away by using a wire cutting machine to obtain C shown in figure 4f/Al-Al/Al3Small samples of Ti layered composites. FIG. 5 is an SEM photograph of a cross section of a Ti-Al based intermetallic compound layered composite material. As can be seen in FIG. 5, in the laminated weave CfIn the/Al composite material layer, the carbon fibers are uniformly distributed in the aluminum matrix; in the presence of Al/Al3In the Ti intermetallic compound composite material layer, Al and Ti react sufficiently to form Al3Ti and in Al3A small amount of aluminum exists in Ti, and the defects of micro cracks, pores and the like do not exist at the interface joint of the two layers of composite materials, which indicates that the interface joint is good.
The Ti-Al intermetallic compound layered composite material can be used as an armor protection material by utilizing the properties of high impact resistance, low areal density and the like of the Ti-Al intermetallic compound layered composite material. For example, the 92-wheel armored vehicle has weak protection capability and can be worn once, so that the C can be embedded or hung at an important part of the armored vehicle on the premise of ensuring the maneuverability of the armored vehiclef/Al-Al/Al3The Ti layered composite material improves the protection capability of the 92-wheel armored vehicle.
The embodiments described above are merely preferred embodiments of the invention, rather than all possible embodiments of the invention. Any obvious modifications to the above would be obvious to those of ordinary skill in the art, but would not bring the invention so modified beyond the spirit and scope of the present invention.

Claims (10)

1. Hot isostatic pressing sintering Cf/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: comprises the following steps:
s1, designing a woven fiber C according to the surface density requirement of the composite materialfThe thickness and the number of layers of fiber cloth and aluminum foil/plate in the Al composite material layer are designed3The thickness and the number of layers of aluminum foil/plate and titanium foil/plate in the Ti intermetallic compound composite material layer;
s2, cutting the materials such as the fiber cloth, the aluminum foil/plate, the titanium foil/plate and the like in the step S1 into the same design size, then arranging the materials in a certain sequence after treatment, loading the arranged materials into a low-carbon steel sheath, then flattening and sealing an exhaust tube after the sheath is pumped into high vacuum, and finally placing the sheath into a hot isostatic pressing furnace for hot pressing and sintering to obtain the Cf/Al-Al/Al3A Ti layered composite material.
2. The C of claim 1f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the areal density of the composite material in the step S1 is 18-32 kg/m2。
3. C according to claim 2f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the fiber cloth in the step S1 is any one of woven materials of carbon fibers, glass fibers or other high-temperature-resistant fibers, and the thickness of the fiber cloth is 0.1-2 mm; the aluminum foil/plate is a pure aluminum foil or plate with the thickness of 0.1-4 mm; the titanium foil/plate is foil or plate of pure titanium or titanium alloy (Ti-6Al-4V), and the thickness is 0.1-2 mm.
4. C according to claim 3f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: in step S1, fiber C is wovenfThe number of layers of the fiber cloth and the aluminum foil/plate in the/Al composite material layer is 4-15; Al/Al3The number of layers of the aluminum foil/plate and the titanium foil/plate in the Ti intermetallic compound composite material layer is 4-15.
5. C according to claim 4f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: polishing the aluminum foil and the titanium foil which are obtained by cutting in the step S2 by using 1500-mesh abrasive paper, then respectively placing the aluminum foil and the titanium foil into deionized water and absolute ethyl alcohol for ultrasonic treatment for 30min, naturally airing the aluminum foil and the titanium foil, and then placing the aluminum foil and the titanium foil into a vacuum drying oven for drying at 50 ℃; and respectively putting the cut fiber cloth into deionized and absolute ethyl alcohol for ultrasonic treatment for 30min, naturally airing, and then putting into a vacuum drying oven for drying at 50 ℃.
6. C according to claim 5f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the arranging in a certain order in step S2 is to arrange the titanium foils/plates and the aluminum foils/plates in a periodic alternating arrangement, then arrange the fiber cloths and the aluminum foils/plates in a periodic alternating arrangement, then stack the two groups of arranged materials together, and finally arrange a layer of titanium foils/plates on the outer layer of the aluminum foils/plates.
7. C according to claim 6f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the low-carbon steel refers to common steel with the carbon content lower than 0.35%, the sheath is a totally-enclosed common steel shell determined according to the size of the sample, and the gap between the interior of the sheath and the sample is required to be less than 1 mm.
8. The C of claim 7f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the high vacuum pumping of the sheath means that the pressure in the sheath is less than 510-3Pa。
9. C according to claim 1f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the step S2 of flattening and sealing the exhaust tube means that after the vacuum pumping in the sheath reaches the required vacuum degree, the exhaust tube near the sheath is heated to be softened by heating means such as acetylene flame, butane flame, electromagnetic induction coil and the like, then 3-4 impressions are flattened on the heating and softening exhaust tube by a hydraulic clamp for sealing, finally, the end of the flattened exhaust tube is cut off by a toothless saw, and the end cut off is welded by an argon arc welding machine immediately, so that air in the atmosphere is prevented from entering the sheath.
10. C according to claim 9f/Al-Al/Al3The preparation method of the Ti layered composite material is characterized by comprising the following steps: the sintering process in the hot isostatic pressing furnace in step S2 is: heating the hearth from 25 ℃ to 600 ℃ at a speed of 10-15 ℃/min, and introducing high-purity argon into the hearth to enable the pressure in the hearth to reach 100MPa-120 MPa; raising the temperature of the hearth to 700-720 ℃ at 3-5 ℃/min, introducing high-purity argon into the hearth to raise the pressure in the hearth to 150-200 Mpa, wherein the final highest temperature, highest pressure and heating and pressurizing time depend on the type of a sample and the size of the sample; thirdly, keeping the temperature and the pressure unchanged under the conditions of highest temperature and highest pressure, wherein the duration time is 2-3 hours; fourthly, slowly reducing the temperature and the pressure to the normal temperature and the normal pressure state after preserving the heat and the pressure.
CN202210460758.8A 2022-04-28 2022-04-28 Hot isostatic pressing sintering C f /Al-Al/Al 3 Preparation method of Ti layered composite material Active CN114771053B (en)

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060147333A1 (en) * 2004-12-30 2006-07-06 Advance Materials Products, Inc. (Admc Products, Inc.) Process of direct powder rolling of blended titanium alloys, titanium matrix composites, and titanium aluminides
CN101011706A (en) * 2007-01-31 2007-08-08 哈尔滨工业大学 Method for composite preparation of Ti alloy/TiAl alloy composite plate material by using laminated rolling-diffusion method
US20090041609A1 (en) * 2007-08-07 2009-02-12 Duz Volodymyr A High-strength discontinuously-reinforced titanium matrix composites and method for manufacturing the same
CN103757453A (en) * 2013-12-19 2014-04-30 陕西理工学院 Ti3AlC2-Ti2AlC/TiAl-based composite material and preparation method thereof
CN106521368A (en) * 2016-12-21 2017-03-22 哈尔滨工业大学 Fiber-reinforced Ti/Al laminar composite material and preparation method thereof
CN106584966A (en) * 2016-12-21 2017-04-26 哈尔滨工业大学 Ti/Al/Cf layered composite material and preparation method thereof
CN108312665A (en) * 2018-02-06 2018-07-24 哈尔滨工业大学 The preparation method of multilevel hierarchy Ti-Al-Cf laminar composites
CN110230012A (en) * 2019-07-08 2019-09-13 南昌航空大学 A kind of vacuum gas pressure infiltration manufacturing process of fiber reinforced aluminum matrix composites

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060147333A1 (en) * 2004-12-30 2006-07-06 Advance Materials Products, Inc. (Admc Products, Inc.) Process of direct powder rolling of blended titanium alloys, titanium matrix composites, and titanium aluminides
CN101011706A (en) * 2007-01-31 2007-08-08 哈尔滨工业大学 Method for composite preparation of Ti alloy/TiAl alloy composite plate material by using laminated rolling-diffusion method
US20090041609A1 (en) * 2007-08-07 2009-02-12 Duz Volodymyr A High-strength discontinuously-reinforced titanium matrix composites and method for manufacturing the same
CN103757453A (en) * 2013-12-19 2014-04-30 陕西理工学院 Ti3AlC2-Ti2AlC/TiAl-based composite material and preparation method thereof
CN106521368A (en) * 2016-12-21 2017-03-22 哈尔滨工业大学 Fiber-reinforced Ti/Al laminar composite material and preparation method thereof
CN106584966A (en) * 2016-12-21 2017-04-26 哈尔滨工业大学 Ti/Al/Cf layered composite material and preparation method thereof
CN108312665A (en) * 2018-02-06 2018-07-24 哈尔滨工业大学 The preparation method of multilevel hierarchy Ti-Al-Cf laminar composites
CN110230012A (en) * 2019-07-08 2019-09-13 南昌航空大学 A kind of vacuum gas pressure infiltration manufacturing process of fiber reinforced aluminum matrix composites

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